Piezoelectric damping rings

ABSTRACT

A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.

CROSS-REFERENCE TO RELATED U.S. APPLICATION

This application is a continuation-in-part of U.S. patent applicationSer. No. 14/845,478 filed 4 Sep. 2015, which claims priority to and thebenefit of U.S. Provisional Patent Application 62/048,071, filed 9 Sep.2014, the original disclosures of both cross-referenced applications arenow expressly incorporated herein by reference.

FIELD OF THE DISCLOSURE

The present disclosure relates generally to turbofan engines, includingbut not limited to those used in propulsion drive systems, such asaircrafts. More specifically, the present disclosure relates to usingpiezoelectric damping rings for use in turbomachinery blisks (i.e.,bladed disks) for dampening vibrations.

BACKGROUND

Gas turbine engines can be used as a primary power source to poweraircraft, watercraft, and other types of vehicles, as well as powergenerators and the like. For example, aerospace applications of gasturbine engines include turboshaft, turboprop, and turbofan engines. Gasturbine engines typically include one or more compressors, a combustor,and one or more turbines. In typical aerospace applications, a fan orpropeller is used to provide the majority of the engine thrust and islocated in front of the core engine. The compressor, in which inlet airis compressed, includes alternating stages of rotating blades and staticvanes, which increase the pressure of the air as it travels through thegas turbine core.

The compressor outputs higher-pressure air, which it delivers to thecombustor, wherein fuel is combusted with the compressed air. As aresult, exhaust gas is generated and directed to the one or moreturbines, wherein the exhaust gas can be used to rotate one or morerotating disks with blades integrally attached. In typical aerospaceapplications, the gas turbine engine provides thrust to propel theaircraft, and also supplies power for accessories of the engine and/orthe aircraft. Accordingly, such integrally bladed rotors, or blisks(i.e., bladed disks), can additionally and/or alternatively be used forother components of the gas turbine engines, such as compressors, fanblade rotors, etc.

Each blisk consists of a single element combining both a rotor disk andblades, as opposed to a disk and a plurality of individual, removableblades. Typically, during operation of turbofan engines, vibration, suchas harmonic vibration from the blades of the blisk, is introduced. Suchvibration may introduce engine wear, thereby reducing engine life.Accordingly, such blisks are generally required to undergo harmonicvibration testing. Conventional technologies to mitigate the vibrationsinclude damping rings, which may be used on blisks of turbofan engines,to reduce or otherwise dampen such vibration when relative motion existson the disk rim and the damping ring, for example.

SUMMARY

The present disclosure may comprise one or more of the followingfeatures and combinations thereof.

According to one aspect of the present disclosure, a blisk assemblyadapted for use in a gas turbine engine includes a disk extendingcircumferentially about a central axis of the blisk assembly, whereinthe disk includes a groove that extends circumferentially about aportion of the disk axisymmetric about the central axis, and wherein thegroove is substantially concave in shape. The blisk assemblyadditionally includes a plurality of blades integrally coupled to thedisk that extend outwardly from the disk in a radial direction away fromthe central axis. The blisk assembly further includes a piezoelectricdamping ring that includes a damping ring and a plurality ofpiezoelectric elements coupled to the damping ring. The piezoelectricdamping ring extends substantially around the central axis within thegroove and each of the piezoelectric elements is configured to convertelectrical energy in response to generation of mechanical energy and toconvert received electrical energy to mechanical energy in response toreceipt of electrical energy from another of the piezoelectric elementsso that vibrations of the blisk assembly are dampened by distribution ofenergy across one or more of the piezoelectric elements.

In some embodiments, the blisk assembly may further include a pluralityof wires, wherein each wire connects at least two of the plurality ofpiezoelectric elements to each other to transmit the electricitytherebetween.

In some embodiments, the blisk assembly may further include anotherpiezoelectric damping ring that is located in another groove thatextends circumferentially about another portion of the disk axisymmetricaround the central axis.

In some embodiments, each of the piezoelectric elements are coupled tothe damping ring using discrete bonding.

In some embodiments, each of the piezoelectric elements includes a metalspray coating to provide an electrically conductive means to send andreceive power.

In some embodiments, each of the piezoelectric elements are comprised ofceramic composite material.

In some embodiments, the plurality of piezoelectric elements comprises afirst and second piezoelectric element, wherein each of the first andsecond piezoelectric elements are connected via a wire, wherein thefirst piezoelectric element is configured to transmit electricityconverted from mechanical energy received at the first piezoelectricelement to the second piezoelectric element.

In some embodiments, the first and second piezoelectric elements arecoupled to the damping ring in different locations along the dampingring to send and received vibration from different nodal diameterpatterns.

In some embodiments, each of the piezoelectric elements arecircumferentially spaced an equidistant amount from neighboringpiezoelectric elements.

In some embodiments, each of the piezoelectric elements is connected toanother of the piezoelectric elements via a wire.

In some embodiments, every other of the piezoelectric elements isconnected to another of the piezoelectric elements via a wire.

In some embodiments, the groove defines a radially inwardly openingchannel.

According to yet another aspect of the present disclosure, apiezoelectric damping ring assembly adapted for use in a blisk of a gasturbine engine, the piezoelectric damping ring includes a damping ringthat extends circumferentially about a central axis and a plurality ofpiezoelectric elements coupled to a surface of the damping ring thatfaces the central axis, wherein each of the piezoelectric elements areequally spaced about the damping ring, and wherein each of thepiezoelectric elements are configured to (i) receive mechanical energy,(ii) convert the stored mechanical energy to electricity, (iii) transmitthe electricity to another of the piezoelectric elements, (iv) receiveconverted electricity from another of the piezoelectric elements, and(v) convert the received converted electricity to mechanical energy todampen vibrations of the blisk.

In some embodiments, the piezoelectric damping ring assembly includes aplurality of wires, wherein each wire connects at least two of theplurality of piezoelectric elements to each other to transmitelectricity therebetween.

In some embodiments, each of the piezoelectric elements are coupled tothe damping ring using discrete bonding.

In some embodiments, each of the piezoelectric elements are comprised ofceramic composite material and wherein each of the piezoelectricelements includes a metal spray coating to provide an electricallyconductive means to send and receive power.

According to still another aspect of the present disclosure, a method ofvibration damping of a blisk adapted for use in a gas turbine engineincludes providing a piezoelectric damping ring in a groove extendingoutward in a radial direction from a radially inward facing surface of adisk portion of the blisk, wherein the groove extends circumferentiallyabout a portion of the disk axisymmetric around a central axis of theblisk, and wherein the piezoelectric damping ring comprises a dampingring and a plurality of piezoelectric elements coupled to the dampingring, rotating the blisk to generate centrifugal force on thepiezoelectric damping ring to generate micro-sleep between thepiezoelectric damping ring and the disk, transferring electricity from afirst piezoelectric element of the plurality of piezoelectric elementsto a second piezoelectric element of the plurality of piezoelectricelements, and dampening vibrations of the blisk as a function of theelectricity received at the second piezoelectric element.

In some embodiments, transferring the electricity from the firstpiezoelectric element to the second piezoelectric element includescapturing mechanical energy at the first piezoelectric element as aproduct of the micro-slip between the piezoelectric damping ring and thedisk, converting the mechanical energy to electricity at the firstpiezoelectric element, transmitting, via a wire coupling the firstpiezoelectric element to the second piezoelectric element, theelectricity from the first piezoelectric element to the secondpiezoelectric element, and converting the electricity to mechanicalenergy at the second piezoelectric element.

In some embodiments, dissipating the mechanical energy at the secondpiezoelectric element comprises dissipating the mechanical energy as aproduct of mechanical friction between the piezoelectric damping ringand the disk.

In some embodiments, the method further includes dissipating themechanical energy through heat due to mechanical friction at the secondpiezoelectric element.

According to another aspect of the present disclosure, further bliskassemblies adapted for use in gas turbine engine are described. Bliskassemblies in accordance with these embodiments may include a diskextending circumferentially about a central axis of the blisk assembly,a plurality of blades integrally coupled to the disk that extendoutwardly from the disk in a radial direction away from the centralaxis, and a piezoelectric damping ring that includes a damping ring anda plurality of piezoelectric elements coupled to the damping ring.

In illustrative embodiments, the piezoelectric damping ring may form afull hoop around the central axis. Each of the piezoelectric elementsincluded in the piezoelectric damping ring may be configured to convertelectrical energy in response to generation of mechanical energy. Eachof the piezoelectric elements included in the piezoelectric damping ringmay also be configured to convert received electrical energy tomechanical energy in response to receipt of the electrical energy fromanother of the piezoelectric elements. Accordingly vibrations of theblisk assembly may be dampened by distribution of energy across one ormore of the piezoelectric elements.

These and other features of the present disclosure will become moreapparent from the following description of the illustrative embodiments.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a cutaway view of a gas turbine engine including a compressorupstream of a combustor for providing compressed air to the combustorand showing that the compressor includes one or more blisks arrangedtherein;

FIG. 2 is a perspective view of one blisk included in the compressor ofFIG. 1 showing a single element assembly comprising a disk and aplurality of blades integrally oriented about outer portion of the diskand a groove extending circumferentially about the underside of thedisk;

FIG. 3 is a perspective view of the blisk of FIG. 2 showing that thegroove includes a piezoelectric damping ring mounted therein;

FIG. 4 is a cross-section view of a portion of the disk showing thegroove including the piezoelectric damping ring of FIG. 3;

FIG. 5 is an illustration of a Campbell diagram that illustrates theoperational behavior during operating modes of the gas turbine engine ofFIG. 1;

FIG. 6 is a cross-section view of a second blisk assembly adapted foruse in a compressor showing that the second blisk assembly includesintegrated disk, platform, and blades that form a blisk along with apiezoelectric damping ring for damping vibrations induced in the bliskduring use, and showing that the piezoelectric damping ring is fastenedto a flange formed by the disk portion and contacts the platform of theblisk near a mid-span region of the blades;

FIG. 7 is a rear elevation view of the second blisk assembly of FIG. 6showing the piezoelectric damping ring includes a full hoop damping ringfastened to the blisk and a plurality of piezoelectric elements coupledto the full hoop damping ring;

FIG. 8 is a cross-section view of a third blisk assembly adapted for usein a compressor, similar to that shown in FIGS. 6 and 7, showing thatthe third blisk assembly includes integrated disk, platform, and bladesthat form a blisk along with a piezoelectric damping ring for dampingvibrations induced in the blisk during use, and showing that thepiezoelectric damping ring is fastened to a bend formed by the disk ofthe blisk and contacts the platform of the blisk at an aft end of theplatform;

FIG. 9 is a cross-section view of a fourth blisk assembly adapted foruse in a compressor, similar to that shown in FIGS. 6 and 7, showingthat the fourth blisk assembly includes integrated disk, platform, andblades that form a blisk along with a piezoelectric damping ring fordamping vibrations induced in the blisk during use, and showing that thepiezoelectric damping ring is fastened to a flange formed by the disk ofthe blisk and contacts the platform of the blisk at an aft end;

FIG. 10 is a cross-section view of a fifth blisk assembly adapted foruse in a compressor, similar to that shown in FIGS. 6 and 7, showingthat the fifth blisk assembly includes integrated disk, platform, andblades that form a blisk along with a piezoelectric damping ring fordamping vibrations induced in the blisk during use, and showing that thepiezoelectric damping ring is fastened to a flange formed by the disk ofthe blisk and contacts the platform portion at a forward end; and

FIG. 11 is a cross-section view of a sixth blisk assembly adapted foruse in a compressor, similar to that shown in FIGS. 6 and 7, showingthat the sixth blisk assembly includes integrated disk, platform, andblades that form a blisk along with a piezoelectric damping ring fordamping vibrations induced in the blisk during use, and showing that thepiezoelectric damping ring is fastened to a drive arm of the disk andcontacts the platform portion at a forward end.

DETAILED DESCRIPTION OF THE DRAWINGS

For the purposes of promoting an understanding of the principles of thedisclosure, reference will now be made to a number of illustrativeembodiments illustrated in the drawings and specific language will beused to describe the same.

An illustrative gas turbine engine 100 for use in aircraft includes anair intake 102, a compressor 104, a combustor 106, and a turbine 108.The compressor 104 may be used to compress air drawn into the air intake102 of the gas turbine engine 100 by a fan 110, which delivers at leasta portion of intake air into the compressor 104. The compressor 104 maybe comprised of one or more compressors configured to provide thecompressed air (i.e., high pressure air) to the combustor 106. Theillustrative compressor includes an intermediate pressure compressor 116and a high pressure compressor 118.

In the combustor 106, fuel is mixed with the high pressure air and isignited, the products (e.g., exhaust gases) of which are directed intothe turbine 108 where energy is extracted to drive the compressor 104and, typically, one or more shafts of the turbine 108 (e.g., forpowering the fan 110). In some embodiments, the turbine 108 may includea low power turbine, an intermediate power turbine, and/or a high powerturbine, each of which may be single or multi-stage turbines. In otherembodiments, such as in steam turbine applications, for example, theturbine 108 may additionally or alternatively include a low pressureturbine, an intermediate pressure turbine, and/or a high pressureturbine, each of which may be single or multi-stage turbines.

In the illustrative gas turbine engine 100, one or more blisks 112, orbladed disks, also commonly referred to as integrally bladed rotors(IBRs), are illustratively shown in the compressor 104 of the gasturbine engine 100 extending around a central axis 114 of the gasturbine engine 100. It should be appreciated that, in some embodiments,the blisks 112 may be located in additional and/or alternativelocations, such as the fan 110, the turbine 108, or any other rotatingcomponent of the gas turbine engine 100.

As shown in FIG. 2, the illustrative blisk 112 includes a plurality ofblades 204 integrally coupled circumferentially about an outer side of arotor disk 202 that is capable of being coupled to a shaft of a rotorassembly of a rotary mechanical device (e.g., a power turbine shaft (notshown) of the gas turbine engine 100). The blisk may be comprised of asingle, solid piece of material that includes a disk portion and aplurality of blades extending therefrom, thereby eliminating the use ofscrews, bolts, or other coupling materials typically used to attachblades to a disk. Accordingly, various manufacturing processes may beused to manufacture the blisk 112; however, such processes are beyondthe scope of the present application. For example, in some embodiments,one or more of the blades may be welded onto the disk portion of theblisks 112.

The illustrative blisk 112 additionally includes a groove 206 on theunderside of the disk 202. In some embodiments, the groove 206 may belocated on a thin portion extending outwardly from the disk 202 (e.g., alip extending from the disk 202). The groove 206 has a generally concaveshape that extends circumferentially about the central axis 114 on theunderside of the disk 202. The groove 206 includes an opening 208 and asurface 210, or recessed portion. As shown in FIG. 3, the groove 206 isconfigured to receive a piezoelectric damping ring 300 coupled to, orotherwise in relative contact to, the surface 210 of the groove 206. Itshould be appreciated that, in some embodiments, rotational loads mayhold the piezoelectric damping ring 300 in place within the groove 206.

Referring now to FIG. 3, the groove 206 is shown that includes anillustrative embodiment of the piezoelectric damping ring 300 coupledthereto. The illustrative piezoelectric damping ring 300 includes adamping ring 302 and a plurality of piezoelectric elements 304 coupledto the damping ring 302. In use, as described in further detail below,the piezoelectric damping ring 300 is capable of providing additionaldamping over traditional damping rings. For example, the piezoelectricdamping ring 300 may be used to further reduce vibration by transferringelectricity across piezoelectric elements, as described in furtherdetail below, such as may be generated when relative motion (e.g.,micro-slip) exists between the disk 202 and the damping ring 302.Accordingly, the damping ring 302 should be manufactured using a metal(e.g., brass or other like soft metal) softer than the metal of theblisk 112, such that the damping ring 302 cannot wear through the disk202. In other words, the sacrificial material should be the damping ring302 and not the blisk 112.

The damping ring 302 includes an outward facing portion 308 and ininward facing portion 310, as well as a split 312. As shown, the outwardfacing portion 308 is coupled to at least a portion of the surface 210of the groove 206. In other words, 360° of the damping ring 302, withthe exception of the split 312, touches the surface 210 of the groove206. Accordingly, mechanical damping may be accomplished by micro-slipgenerated between the damping ring 302 and the disk 202, which canresult from different spring constants of the blisk 112 and the dampingring 302 reflecting differently.

The piezoelectric damping ring 300 includes a plurality of piezoelectricelements 304, each of which are coupled to the damping ring 302 atdifferent circumferential locations about the inward facing portion 310of the damping ring 302 at an outward facing portion 314 of thepiezoelectric elements 304. It should be appreciated that any knowntechnology may be used to couple the piezoelectric elements 304 to thedamping ring 302. For example, in some embodiments, the piezoelectricelements 304 may be discretely bonded to the damping ring 302.Additionally or alternatively, in some embodiments, a thin metal spraycoating may be applied to each of the piezoelectric elements 304 toprotect the piezoelectric elements from adverse conditions (e.g.,particulate matter) and provide an electrically conductive means to sendand receive power. Additionally, each of the piezoelectric elements 304may be made of any suitable material capable of performing the functionsdescribed herein, such as ceramic strips bonded to the damping ring 302,for example. Accordingly, in such an embodiment, the piezoelectricdamping ring 300 may additionally dissipate heat.

As described previously, if one of the piezoelectric elements 304 of thepiezoelectric damping ring 300 becomes excited by motion, mechanicalenergy may be received by that excited piezoelectric element 304. Thismay cause the piezoelectric damping ring 300 to vibrate at another partof the piezoelectric damping ring 300 due to electrical connectionsbetween different circumferential positions. The piezoelectric dampingring 300 may then slowly rotate relative to the blisk 112 or slowlyrotate relative to a stationary vane, such as in a snake like motion.This relative movement may cause additional friction damping, creatingheat, which can be dissipated at least partially, such as by creatingmechanical friction between the piezoelectric damping ring 300 and thegroove 206 of the disk 202. To do so, as also described previously, themechanical energy received by the excited piezoelectric element 304 canbe converted to electricity, which can then be transmitted to another ofthe piezoelectric elements 304 connected to the excited piezoelectricelement 304 and dissipated at the other piezoelectric element 304.

The illustrative piezoelectric damping ring 300 includes sixteenpiezoelectric elements 304 coupled to the damping ring 302. Inalternative piezoelectric damping ring embodiments, additional and/orfewer piezoelectric elements 304 may be coupled to the damping ring 302.As shown, every other of the piezoelectric elements 304 is paired (i.e.,connected) at an inward facing surface 316 via a wire 306 to another ofthe piezoelectric elements 304 at the inward facing surface 316 of thatone of the piezoelectric elements 304. In such an embodiment as theillustrative embodiment of FIG. 3, the piezoelectric damping ring 300may support eight engine orders (i.e., N/2, wherein “N” represents thenumber of piezoelectric elements 304 and “2” designates the number ofneighboring piezoelectric elements 304 from which the piezoelectricelement 304 is wired), or eight nodal diameters. Accordingly, differentengine orders may be supported based on the number of and theinterconnectivity between (see, e.g., the wiring 306) the piezoelectricelements 304 of the piezoelectric damping ring 300.

To do so, one of the connected piezoelectric elements 304 may be excitedby the electricity from another of the piezoelectric elements 304 thatit has been connected to via the wiring 306. For example, as a result ofmicro-slip, mechanical energy at one of the piezoelectric elements 304at one engine order can be converted to electrical energy andtransmitted to another of the piezoelectric elements 304 at a differentengine order via mechanical friction and dissipated through heat. Inuse, the electrical energy can be transferred from an active crossing(see, e.g., the active crossing 510 of FIG. 5) to an inactive crossing(e.g., a crossing at a different engine order).

It should be appreciated that additional and/or alternative wiringmethods may be used to support additional engine orders. For example, inalternative embodiments, the wiring 306 may connect to different ends ofthe piezoelectric elements 304 (e.g., positively and negatively chargedportions of the piezoelectric elements 304) and/or the middle of thepiezoelectric elements 304 as shown in FIG. 3. Additionally oralternatively, in some embodiments, the underlying blisk 112 may be usedas a conductive means to transfer electricity from one piezoelectricelement 304 to another piezoelectric element 304.

Accordingly, the wiring 306 running between of the piezoelectricelements 304 at different locations can facilitate the flow ofelectricity from one of the piezoelectric elements 304 to dissipate theenergy through mechanical damping at another one of the piezoelectricelements 304 that is out of phase with the other of the piezoelectricelements 304. In other words,

mechanical energy may be extracted from a first piezoelectric element304 at a first nodal diameter pattern, which can be used to excite thepiezoelectric damping ring 300 into a second nodal diameter pattern.Accordingly, the second nodal diameter pattern of the ring may thendissipate energy through friction (i.e., generating heat). For example,if one of the piezoelectric elements 304 at a first position createsmotion out of phase with the motion of a connected other of thepiezoelectric elements 304 at a second position, transferringelectricity converted from the mechanical energy can be used to cancelout vibration (e.g., via mechanical friction dissipated as heat).

It should be appreciated that, in some embodiments, more than onepiezoelectric damping ring 300 may be included, either in the samegroove 206 adjacent to another piezoelectric damping ring 300 or belocated in another groove such that each of the piezoelectric dampingrings 300 are axisymmetric around the central axis 114 (i.e., the enginecenterline). For example, as shown in FIG. 4, the groove 206 of FIGS. 2and 3 is positioned upstream of another groove 402, which is positioneddownstream of the groove 206 at a position that is axisymmetric aboutthe central axis 114.

It should be appreciated that, in some embodiments, one or more of thepiezoelectric elements 304 may be connected across resistive elements togenerate heat, or power a device, for example. In other words, one ormore of the piezoelectric elements 304 can double as damping elementswhose additional energy can be used to power other devices of the gasturbine engine 100.

Referring now to FIG. 5, an illustrative Campbell diagram 500 showsexample behavior a fan measured in the environment of an engine (e.g.,of the fan 110 of the gas turbine engine 100 of FIG. 1) during differentoperating modes. The Campbell diagram 500 includes a frequency in Hertzaxis along a y-axis 502, a speed in revolutions per minute (RPM) alongan x-axis 504, and a number of engine order (EO) lines 506. The Campbelldiagram 500 additionally includes output of various modes 508 of the gasturbine engine 100 at increasing operational frequencies and speeds.

As shown, Mode 4 and the seventh engine (i.e., 7EO) order crossing couldenergize a damping ring in the seventh nodal diameter. In such anembodiment, the piezoelectric elements 304 of the piezoelectric dampingring 300 may be wired to transmit the seventh engine order energy toanother engine order that does not have any crossings in the runningrange of the engine. Accordingly, the seventh order energy can beconverted to electricity and transmitted to another piezoelectricelement 304 at a different nodal diameter, such that the electricity maybe used to dampen vibration by inducing micro-slip between thepiezoelectric damping ring 300 and the disk 202. In other words, thepiezoelectric damping ring 300 can be excited by the resultingelectricity into another nodal diameter with a crossing outside therunning speed of the engine (e.g., the gas turbine engine 100) wheremicro-slip between the blisk and the piezoelectric damping ring woulddissipate the energy (i.e., between the damping ring 302 of thepiezoelectric damping ring 300 and the surface 210 of the disk 202).

A second blisk assembly 2000 in accordance with the present disclosureis shown in FIGS. 6 and 7. The blisk assembly 2000 includes a blisk 2112and a piezoelectric damping ring 2300. The blisk 2112 is an integrallybladed disk or rotor similar to blisk 112 described above. Thepiezoelectric damping ring 2300 is coupled to the blisk 2112 and dampensvibration of the blisk assembly 2000 during use in a gas turbine enginelike engine 100.

The blisk 2112 illustratively includes a disk 2202, a plurality ofblades 2204, and a platform 2205 that are integrated with one another asshown in FIG. 6. The disk 2202 supports the blades 2204 and the platform2205 during rotation of the blisk 2112. The blades 2204 interact withgasses passing through an engine to compress the gasses. The platform2205 extends forward and aft of the blades 2204 to separate the disk2202 from the plurality of blades 2204 so that gasses passing over theblades 2204 does not interact with the disk 2202.

The disk 2202 illustratively includes a drive arm 2220, a cone shaft2222, a support ring 2224, and a damper flange 2225 as shown in FIG. 6.The drive arm 2220 is configured to be coupled to a shaft to receiverotation from other parts of an engine. The cone shaft 2222 extendsoutwardly from the drive arm 2220 to the support ring 2224. The supportring 2224 supports the blades 2204 and the platform 2205. The damperflange 2225 is cantilevered and provides a location for coupling of thepiezoelectric damping ring 2300.

The piezoelectric damping ring 2300 illustratively includes a dampingring 2302, piezoelectric elements 2304, and wires 2306 as shown in FIGS.6 and 7. The damping ring 2302 is a full hoop component that extendsaround a central axis 2114. The piezoelectric elements 2304 are coupledto the damping ring 2302 and are equidistantly spaced from one anothercircumferentially around the axis 2114.

In the illustrative embodiment, the damping ring 2302 is fastened to thedamper flange 2225 by bolts along an inner portion of the damper ring2302 as shown in FIG. 6. The damping ring 2303 contacts the platform2205 near a mid-span of the blades 2204 along an outer portion of thedamper ring 2302 where the damper ring 2302 is free for micro movementsrelative to the blisk 2112. In the illustrative embodiments, thepiezoelectric elements 2304 are coupled to the damping ring 2302 along amiddle portion of the damper ring 2302 between the inner and outerportions.

The piezoelectric elements 2304 are substantially similar to elements304 and pass energy from one to another via wires 2306 as describedherein. As described herein, the piezoelectric elements 2304 can dampenvibration in the blisk assembly 2000.

A third blisk assembly 3000 in accordance with the present disclosure isshown in FIG. 8. The blisk assembly 3000 includes a blisk 3112 and apiezoelectric damping ring 3300. The blisk 3112 is an integrally bladeddisk or rotor similar to blisk 112 described above. The piezoelectricdamping ring 3300 is coupled to the blisk 3112 and dampens vibration ofthe blisk assembly 3000 during use in a gas turbine engine like engine100.

The blisk 3112 illustratively includes a disk 3202, a plurality ofblades 3204, and a platform 3205 that are integrated with one another asshown in FIG. 8. The disk 3202 supports the blades 3204 and the platform3205 during rotation of the blisk 3112. The blades 3204 interact withgasses passing through an engine to compress the gasses. The platform3205 extends forward and aft of the blades 3204 to separate the disk3202 from the plurality of blades 3204 so that gasses passing over theblades 3204 does not interact with the disk 3202.

The disk 3202 illustratively includes a drive arm 3220, a cone shaft3222, a support ring 3224, and a damper flange 3225 as shown in FIG. 8.The drive arm 3220 is configured to be coupled to a shaft to receiverotation from other parts of an engine. The cone shaft 3222 extendsoutwardly from the drive arm 3220 to the support ring 3224. The supportring 3224 supports the blades 3204 and the platform 3205. The damperflange 3225 interconnects the cone shaft 3222 and the SUPPORT RING 3224.The damper flange 3225 also provides a location for coupling of thepiezoelectric damping ring 3300.

The piezoelectric damping ring 3300 illustratively includes a dampingring 3302, piezoelectric elements 3304, and wires as shown in FIG. 8.The damping ring 3302 is a full hoop component. The piezoelectricelements 3304 are coupled to the damping ring 3302 and are equidistantlyspaced from one another circumferentially around the axis 3114.

In the illustrative embodiment, the damping ring 3302 is fastened to thedamper flange 3225 by bolts along an inner portion of the damper ring3302 as shown in FIG. 8. The damping ring 3303 contacts the platform3205 near a mid-span of the blades 3204 along an outer portion of thedamper ring 3302 where the damper ring 3302 is free for micro movementsrelative to the blisk 3112. In the illustrative embodiments, thepiezoelectric elements 3304 are coupled to the damping ring 3302 along amiddle portion of the damper ring 3302 between the inner and outerportions.

The piezoelectric elements 3304 are substantially similar to elements304 and pass energy from one to another via wires as described herein.As described herein, the piezoelectric elements 3304 can dampenvibration in the blisk assembly 3000.

A fourth blisk assembly 4000 in accordance with the present disclosureis shown in FIG. 9. The blisk assembly 4000 includes a blisk 4112 and apiezoelectric damping ring 4300. The blisk 4112 is an integrally bladeddisk or rotor similar to blisk 112 described above. The piezoelectricdamping ring 4300 is coupled to the blisk 4112 and dampens vibration ofthe blisk assembly 4000 during use in a gas turbine engine like engine100.

The blisk 4112 illustratively includes a disk 4202, a plurality ofblades 4204, and a platform 4205 that are integrated with one another asshown in FIG. 9. The disk 4202 supports the blades 4204 and the platform4205 during rotation of the blisk 4112. The blades 4204 interact withgasses passing through an engine to compress the gasses. The platform4205 extends forward and aft of the blades 4204 to separate the disk4202 from the plurality of blades 4204 so that gasses passing over theblades 4204 does not interact with the disk 4202.

The disk 4202 illustratively includes a drive arm 4220, a cone shaft4222, a support ring 4224, and a damper flange 4225 as shown in FIG. 9.The drive arm 4220 is configured to be coupled to a shaft to receiverotation from other parts of an engine. The cone shaft 4222 extendsoutwardly from the drive arm 4220 to the support ring 4224. The supportring 4224 supports the blades 4204 and the platform 4205. The damperflange 4225 is cantilevered from the cone shaft 4222 and provides alocation for coupling of the piezoelectric damping ring 4300.

The piezoelectric damping ring 4300 illustratively includes a dampingring 4302, piezoelectric elements 4304, and wires as shown in FIG. 9.The damping ring 4302 is a full hoop component. The piezoelectricelements 4304 are coupled to the damping ring 4302 and are equidistantlyspaced from one another circumferentially around the axis 4114.

In the illustrative embodiment, the damping ring 4302 is fastened to thedamper flange 4225 by bolts along an inner portion of the damper ring4302 as shown in FIG. 9. The damping ring 4303 contacts the platform4205 at an aft end of the platform 4205 along an outer portion of thedamper ring 4302 where the damper ring 4302 is free for micro movementsrelative to the blisk 4112. In the illustrative embodiments, thepiezoelectric elements 4304 are coupled to the damping ring 4302 along amiddle portion of the damper ring 4302 between the inner and outerportions.

The piezoelectric elements 4304 are substantially similar to elements304 and pass energy from one to another via wires as described herein.As described herein, the piezoelectric elements 4304 can dampenvibration in the blisk assembly 4000.

A fifth blisk assembly 5000 in accordance with the present disclosure isshown in FIG. 10. The blisk assembly 5000 includes a blisk 5112 and apiezoelectric damping ring 5300. The blisk 5112 is an integrally bladeddisk or rotor similar to blisk 112 described above. The piezoelectricdamping ring 5300 is coupled to the blisk 5112 and dampens vibration ofthe blisk assembly 5000 during use in a gas turbine engine like engine100.

The blisk 5112 illustratively includes a disk 5202, a plurality ofblades 5204, and a platform 5205 that are integrated with one another asshown in FIG. 10. The disk 5202 supports the blades 5204 and theplatform 5205 during rotation of the blisk 5112. The blades 5204interact with gasses passing through an engine to compress the gasses.The platform 5205 extends forward and aft of the blades 5204 to separatethe disk 5202 from the plurality of blades 5204 so that gasses passingover the blades 5204 does not interact with the disk 5202.

The disk 5202 illustratively includes a drive arm 5220, a cone shaft5222, a support ring 5224, and a damper flange 5225 as shown in FIG. 10.The drive arm 5220 is configured to be coupled to a shaft to receiverotation from other parts of an engine. The cone shaft 5222 extendsoutwardly from the drive arm 5220 to the support ring 5224. The supportring 5224 supports the blades 5204 and the platform 5205. The damperflange 5225 is cantilevered from the support ring 5224 and has anL-shaped cross-sectional shape that extends in a forward direction. Thedamper flange 5225 provides a location for coupling of the piezoelectricdamping ring 5300.

The piezoelectric damping ring 5300 illustratively includes a dampingring 5302, piezoelectric elements 5304, and wires as shown in FIG. 10.The damping ring 5302 is a full hoop component. The piezoelectricelements 5304 are coupled to the damping ring 5302 and are equidistantlyspaced from one another circumferentially around the axis 5114.

In the illustrative embodiment, the damping ring 5302 is fastened to thedamper flange 5225 by bolts along an inner portion of the damper ring5302 as shown in FIG. 10. The damping ring 5303 contacts the platform5205 at a forward end of the platform 5205 along an outer portion of thedamper ring 5302 where the damper ring 5302 is free for micro movementsrelative to the blisk 5112. In the illustrative embodiments, thepiezoelectric elements 5304 are coupled to the damping ring 5302 along amiddle portion of the damper ring 5302 between the inner and outerportions.

The piezoelectric elements 5304 are substantially similar to elements304 and pass energy from one to another via wires as described herein.As described herein, the piezoelectric elements 5304 can dampenvibration in the blisk assembly 5000.

A sixth blisk assembly 6000 in accordance with the present disclosure isshown in FIG. 11. The blisk assembly 6000 includes a blisk 6112 and apiezoelectric damping ring 6300. The blisk 6112 is an integrally bladeddisk or rotor similar to blisk 112 described above. The piezoelectricdamping ring 6300 is coupled to the blisk 6112 and dampens vibration ofthe blisk assembly 6000 during use in a gas turbine engine like engine100.

The blisk 6112 illustratively includes a disk 6202, a plurality ofblades 6204, and a platform 6205 that are integrated with one another asshown in FIG. 11. The disk 6202 supports the blades 6204 and theplatform 6205 during rotation of the blisk 6112. The blades 6204interact with gasses passing through an engine to compress the gasses.The platform 6205 extends forward and aft of the blades 6204 to separatethe disk 6202 from the plurality of blades 6204 so that gasses passingover the blades 6204 does not interact with the disk 6202.

The disk 6202 illustratively includes a drive arm 6220, a cone shaft6222, and a support ring 6224 as shown in FIG. 11. The drive arm 6220 isconfigured to be coupled to a shaft to receive rotation from other partsof an engine. The cone shaft 6222 extends outwardly from the drive arm6220 to the support ring 6224. The support ring 6224 supports the blades6204 and the platform 6205.

The piezoelectric damping ring 6300 illustratively includes a dampingring 6302, piezoelectric elements 6304, and wires as shown in FIG. 11.The damping ring 6302 is a full hoop component. The piezoelectricelements 6304 are coupled to the damping ring 6302 and are equidistantlyspaced from one another circumferentially around the axis 6114.

In the illustrative embodiment, the damping ring 6302 is fastened to thedrive arm 6220 by bolts along an inner portion of the damper ring 6302as shown in FIG. 11. The damping ring 6303 contacts the platform 6205 ata forward end of the platform 6205 along an outer portion of the damperring 6302 where the damper ring 6302 is free for micro movementsrelative to the blisk 6112. In the illustrative embodiments, thepiezoelectric elements 6304 are coupled to the damping ring 6302 along amiddle portion of the damper ring 6302 between the inner and outerportions.

The piezoelectric elements 6304 are substantially similar to elements304 and pass energy from one to another via wires as described herein.As described herein, the piezoelectric elements 6304 can dampenvibration in the blisk assembly 6000.

While the disclosure has been illustrated and described in detail in theforegoing drawings and description, the same is to be considered asexemplary and not restrictive in character, it being understood thatonly illustrative embodiments thereof have been shown and described andthat all changes and modifications that come within the spirit of thedisclosure are desired to be protected.

What is claimed is:
 1. A blisk assembly adapted for use in a gas turbineengine, the blisk assembly comprising a disk extending circumferentiallyabout a central axis of the blisk assembly, a plurality of bladesintegrally coupled to the disk that extend outwardly from the disk in aradial direction away from the central axis, and a piezoelectric dampingring that includes a damping ring and a plurality of piezoelectricelements coupled to the damping ring, wherein the piezoelectric dampingring forms a full hoop around the central axis and each of thepiezoelectric elements is configured to convert electrical energy inresponse to generation of mechanical energy and to convert receivedelectrical energy to mechanical energy in response to receipt of theelectrical energy from another of the piezoelectric elements so thatvibrations of the blisk assembly are dampened by distribution of energyacross one or more of the piezoelectric elements.
 2. The blisk assemblyof claim 1, further comprising a plurality of wires, wherein each wireconnects at least two of the plurality of piezoelectric elements to eachother to transmit electricity therebetween.
 3. The blisk assembly ofclaim 1, wherein the damping ring is coupled to the disk by a pluralityof fasteners at a first radius and the damping ring contacts anotherportion of the blisk assembly at a second radius spaced apart from theplurality of fasters to allow for relative movement of the damping ringrelative to the disk at the second radius.
 4. The blisk assembly ofclaim 3, wherein the second radius is located outward of the firstradius.
 5. The blisk assembly of claim 4, wherein the plurality ofpiezoelectric elements arranged at a third radius spaced apart from thefirst radius to allow for relative movement of the piezoelectricelements relative to the disk.
 6. The blisk assembly of claim 5, whereinthe third radius is located between the first radius and the secondradius.
 7. The blisk assembly of claim 1, wherein each of thepiezoelectric elements are coupled to the damping ring using discretebonding.
 8. The blisk assembly of claim 1, wherein each of thepiezoelectric elements includes a metal spray coating to provide anelectrically conductive means to send and receive power.
 9. The bliskassembly of claim 1, wherein the plurality of piezoelectric elementscomprises a first piezoelectric element and a second piezoelectricelement, wherein each of the first and second piezoelectric elements areconnected via a wire, wherein the first piezoelectric element isconfigured to transmit electricity converted from mechanical energyreceived at the first piezoelectric element to the second piezoelectricelement.
 10. The blisk assembly of claim 9, wherein the first and secondpiezoelectric elements are coupled to the damping ring in differentlocations along the damping ring to send and received vibration fromdifferent nodal diameter patterns.
 11. The blisk assembly of claim 9,wherein each of the piezoelectric elements are circumferentially spacedan equidistant amount from neighboring piezoelectric elements.
 12. Theblisk assembly of claim 1, further comprising a platform integrallyformed with the disk and the plurality of blades that separates the diskfrom the plurality of blades so that gasses passing over the blades doesnot interact with the disk, and wherein the damping ring is coupled tothe disk by a plurality of fasteners at a first radius and the dampingring contacts the platform at a second radius radially outward of theplurality of fasters to allow for relative movement of the damping ringrelative to the disk at the second radius.
 13. The blisk assembly ofclaim 12, wherein the disk is formed to include a cantilevered flange towhich the damping ring is fastened.
 14. The blisk assembly of claim 12,wherein the damping ring contacts the platform near a mid-span of theplurality of blades.
 15. The blisk assembly of claim 12, wherein thedamping ring contacts the platform at an aft end of the platform. 16.The blisk assembly of claim 12, wherein the damping ring contacts theplatform at forward end of the platform.
 17. A method of vibrationdamping of a blisk adapted for use in a gas turbine engine, the methodcomprising providing a piezoelectric damping ring to a disk included inthe blisk, wherein the piezoelectric damping ring comprises a dampingring and a plurality of piezoelectric elements coupled to the dampingring, the damping ring fastened to the disk at a first location andcontacting another portion of the blisk spaced apart from the firstlocation to allow microslip between the damping ring and the rest of theblisk; rotating the blisk to generate centrifugal force on thepiezoelectric damping ring and to generate micro-sleep between thepiezoelectric damping ring and the disk; transferring electricity from afirst piezoelectric element of the plurality of piezoelectric elementsto a second piezoelectric element of the plurality of piezoelectricelements; dampening vibrations of the blisk as a function of theelectricity received at the second piezoelectric element.
 18. The methodof claim 17, wherein transferring the electricity from the firstpiezoelectric element to the second piezoelectric element comprises:capturing mechanical energy at the first piezoelectric element as aproduct of micro-slip between the piezoelectric damping ring and thedisk; converting the mechanical energy to electricity at the firstpiezoelectric element; transmitting, via a wire coupling the firstpiezoelectric element to the second piezoelectric element, theelectricity from the first piezoelectric element to the secondpiezoelectric element; and converting the electricity to mechanicalenergy at the second piezoelectric element.
 19. The method of claim 18,wherein dissipating the mechanical energy at the second piezoelectricelement comprises dissipating the mechanical energy as a product ofmechanical friction between the piezoelectric damping ring and the disk.20. The method of claim 19, further comprising dissipating themechanical energy through heat due to mechanical friction at the secondpiezoelectric element.